Stabilizer for aerial machines.



e. MADEIRIA.

STABILIZER FOR AERIAL MACHINES. APPLICATION FILED JULY 9.191s.

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STABILIZER FO'R AERIAL MACHINES.

APPLICATION FILED JULY 9. 1915.

1,201,210. Patented Oct. 10,1916.

i I 2 SHEETS-SHEET 2- G'Hs TO/V Macs/RH GASTON MADEIRA, OF NEUILLY-SUR-SEINE, FRANCE.

STABILIZER FOR AERIAL MACHINES.

Application filed July 9, 1915.

To all whom it may concern:

Be it known that I, GASTON MADEIRA, a-

chines, in which relative movements of the fuselage and of the engine which is suspended like a pendulum, are utilized forcontrolling the horizontal rudder or rudders.

A construction according to this invention is illustrated in the accompanying drawing, in which,

Figure 1 is a plan of the device for the automatic control of the horizontal rudder; Fig. 1 shows the back part of the device. Fig. 2 shows the arrangement of the engine on the fuselage, with a diagram of movements of the horizontal rudder; Fig. 3 shows a modified'arrangement of the engine on the fuselage; Fig. 4.- is a detail of the mechanism; and Fig. 5 another detail on an enlarged scale.

The engine A is mounted on the fuselage B by means of two trunnions a normal to the longitudinal axis of the fuselage B, so

that, whatever be the incidence of the fuselage, the engine A remains vertical. In order to avoid the production of a tractlon couple the axis of rotation of the propeller must meet the axis of the trunnions a To that end, the engine is mounted (Fig. 2) either with the crank case above, and the cylinders below or (Fig. 3) with the crank case suspended below the propeller shaft, the movement being transmitted from the engine to the propeller by a chaln or the like.

In order to transmit the oscillatory motion of the engine to the horizontal rudder, a double set of bevel wheels is used. To one trunnion a, is keyed a bevel pinion C engaging with a smaller pinion C keyed to the end of a spindle D pivoted on the fuselage at cl. To the other end of the spindle D is keyed a bevel pinion O engaging with a bevel pinion C keyed to the spindle E of the horizontal rudder E The diameters of the pinions C, C C C are calculated so as to magnify the movements of the en- 5 gine to a considerable extent. The spindle D is provided with two Cardan joints d so Specification of Letters Patent.

Serial No. 39,023.

as to enable it to follow deformations of the fuselage without any stiffness in its working. The spindle is moreover divided at the level of the airmans seat, the connection between the rear and the front parts being effected as follows :-To the rear part of the spindle D is keyed a sleeve D on WhlCh is pivoted at f a bell-crank lever F controlled by a spring 7'. The long arm of the bellcrank lever F is within reach of the airman, in order to enable him to control the horizontal rudder independently of the automatic stabilizer. On the front'part of the spindle D is mounted a sleeve D by means of a feather, so that the sleeve can slide. The movements of the sleeve are obtained by a ball governor G and lever G pivoted at 5 to the fuselage. The said sleeve comprises (Fig. 5) a cylindrical portion provided with an inclined groove (l and a disk (l provided with notches with which can engage (when the engine is running, and the balls of the. governor are spread apart) the short arm of the bell-crank lever F. The connection between the two parts of the spindle D is thus obtained. lVhen the engine stops (Fig. 1), the sleeve D is moved forward by the governor G; the short arm of the lever is disengaged from the notches of the disk d and drops into the inclined groove (Z \Vhen the movement of the sleeve continues. the spindle D is rotated, which results in the horizontal rudder being automatically brought into the position which it must occupy during a volplane.

The airman can at will, in every case, do away with the automatic control of the horizontal rudder. by pulling the lever F in the direction of the arrow .12, which disengages the short arm of the lever from the notches of the disk (1 or from the inclined track ti.

The airman can then control the horizontal rudder by turning the lever to the right or left in a vertical plane.

(laimsz 1. In a stabilizer for aeroplanes, a rudder, a two-part spindle controlling the same, a coupling between said spindle parts, a motor and means governed by the motor for imparting to one of said parts an actuating displacement to bring the rudder automatically to wlplane position on the halt of the motor.

2. In a stabilizer for aeroplanes, a rudder, a two-part spindle controlling the same, a manually operated coupling between said Patented Oct. 10, 1916.

spindle parts, a motor and means governed by the motor for imparting to one of said parts an actuating displacement to bring the rudder automatically to "olplane position on the halt of the motor.

'3. In a stabilizer for aeroplanes, a rudder, a two-part spindle controlling the same, a coupling between said spindle parts, a motor and an operative connection between one of said parts and a motor element whereby upon the halt of the motor an actuating displacement of the rudder to volplane position is automatically effected.

4. In a stabilizer for aeroplanes, a rudder, a two-part spindle controlling the same, a coupling between said spindle parts, a motor and a centrifugal governor driven thereby, together with an operative connection between said governor and one of said spindle parts for imparting thereto an actuating displacement to bring the rudder automatically to volplane position on the halt of the motor.

5. In a stabilizer for aeroplanes, a rudder, a spindle controlling the same, a motor, a centrifugal member driven thereby, and a torquing connection between said centrifugal member and spindle for rotating the latter to bring the rudder automatically to vol plane position on the halt of the motor, in combination with manually operated means for breaking the connection between the governor and spindle and operating the latter without respect to the motor.

In testimony whereof I have vsigned my name to this specification, in the presence of two subscribing witnesses.

GASTON MADEIRA.

Witnesses CHAS. P. PRESSLY, U Lyssa DEFiavREMoN'r. 

